US20110168852A1 - Method of depositing a coating for improving laminar flow - Google Patents

Method of depositing a coating for improving laminar flow Download PDF

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Publication number
US20110168852A1
US20110168852A1 US12/996,446 US99644609A US2011168852A1 US 20110168852 A1 US20110168852 A1 US 20110168852A1 US 99644609 A US99644609 A US 99644609A US 2011168852 A1 US2011168852 A1 US 2011168852A1
Authority
US
United States
Prior art keywords
coating
groove
outside surface
theoretical
deposition
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US12/996,446
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English (en)
Inventor
Alain Porte
Philippe Descamps
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Assigned to AIRBUS OPERATIONS SAS reassignment AIRBUS OPERATIONS SAS ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DESCAMPS, PHILIPPE, PORTE, ALAIN
Publication of US20110168852A1 publication Critical patent/US20110168852A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49863—Assembling or joining with prestressing of part
    • Y10T29/49867—Assembling or joining with prestressing of part of skin on frame member
    • Y10T29/49869—Assembling or joining with prestressing of part of skin on frame member by flexing

Definitions

  • This invention relates to a process for deposition of a coating whose purpose is to improve the laminar flow at the junction of a leading edge and an adjacent surface, more particularly suitable for improving the laminar flow at the junction of a lip and an outside surface of a nacelle.
  • FIGS. 1 , 2 and 3 show a nacelle 10 that comprises at least one inside pipe 12 , an outside surface 14 , and, at the front, an air intake that is delimited by a lip 16 that connects the inside pipe 12 and the outside surface 14 .
  • the walls of the inside pipe, the lip, or the outside surface are obtained by the assembly of several panels, several plates, several skins, or the like. Hereinafter, all of these wall forms will be referred to by the term panel.
  • the structure of the nacelle comprises a front frame 18 that connects the outside surface 14 and the inside pipe 12 , and that supports the lip 16 .
  • the front frame 18 comprises a first edge that is arranged at the junction of the outside surface 14 and the lip 16 and a second edge that is arranged at the junction of the inside pipe 12 and the lip 16 .
  • the front frame 18 comprises a support surface 20 at the level of which the outside surface 14 and the lip 16 are made integral using attachment means 22 .
  • the panels of the outside surface 14 and the lip 16 are placed end to end and do not overlap.
  • the attachment means 22 generally rivets that are flush with the aerodynamic surfaces, generate disturbances that tend to increase the drag and consequently the energy consumption of the aircraft.
  • the patent FR-2,787,509 describes rivets that are flush for connecting an acoustic panel to an air intake.
  • the purpose of this invention is to eliminate the drawbacks of the prior art by proposing a process for deposition of a coating for improving the laminar flows at the junction zone between a leading edge and another adjacent surface.
  • the invention has as its object a process for deposition of a coating whose purpose is to improve the laminar flows at a junction between a first panel of a leading edge and a second panel of an adjacent surface according to the direction of said flows, characterized in that it comprises the following stages that consist in:
  • the invention has as its object an aircraft nacelle that comprises an inside pipe, an outside surface, and, at the front, an air intake that is delimited by a lip that connects the inside pipe and the outside surface, characterized in that it comprises, at the junction between said lip and the outside surface, a shallow groove relative to the theoretical continuous surface of said junction, which extends over a width such that the outside surfaces of the panels of said lip and the outside surface do not project further relative to the theoretical surface, and a coating that is arranged in the groove in such a way as to fill it in.
  • FIG. 1 is a perspective view of the front of a nacelle of an aircraft according to the prior art
  • FIG. 2 is a cutaway along a longitudinal plane of a portion of the front of an aircraft nacelle
  • FIG. 3 is a cutaway that illustrates the junction zone of the lip and the outside surface of a nacelle according to the prior art
  • FIG. 4 is a perspective view of the front of a nacelle according to the invention.
  • FIG. 5 is a cutaway that illustrates the junction zone of the lip and the outside surface of a nacelle according to a first variant of the invention
  • FIG. 6 is a cutaway that illustrates the junction zone of the lip and the outside surface of a nacelle according to another variant of the invention.
  • FIGS. 7A and 7C are cutaways that illustrate the different stages of the installation of the coating according to the invention.
  • FIG. 8 is a cutaway along a longitudinal plane of a portion of the front of an aircraft nacelle that illustrates the formation of a stream of air between the outside and the inside of the nacelle.
  • FIGS. 4 , 5 and 6 show a nacelle that comprises an inside pipe 32 , an outside surface 34 , and, at the front, an air intake that is delimited by a lip 36 that connects the inside pipe 32 and the outside surface 34 .
  • the other elements are not shown and described because they are known to one skilled in the art.
  • the inside pipe and the outside surface are obtained by the assembly of several panels, several plates, several skins or the like.
  • all of these wall forms will be referred to by the term panel.
  • the inside pipe, the outside surface, and the lip can be metallic and/or made of a composite material.
  • the wall of the lip is formed by a panel or a panel assembly.
  • the structure of the nacelle comprises a front frame 38 that connects the outside surface 34 and the inside pipe 32 and that supports the lip 36 .
  • the front frame 38 comprises a first edge that is arranged at the junction of the outside surface 34 and the lip 36 and a second edge that is arranged at the junction of the inside pipe 32 and the lip 36 .
  • the front frame 38 comprises a support surface 40 at the level of which the outside surface 34 and the lip 36 are made integral using attachment means 42 , for example one or several series of rivets.
  • attachment means 42 for example one or several series of rivets.
  • At least one wedge 44 can be interposed between the support surface 40 of the front frame and the panel of the outside surface 34 and/or the lip 36 so as to compensate for the possible difference in thickness between the two panels that are placed end to end at the junction zone.
  • the outside surfaces of the panels are not continuous at the junction, in particular because of differences in the curvature radii of the panels that are placed end to end.
  • the theoretical continuous surface 46 of the junction shown in dotted lines on the surface 7 A, and the outside surfaces of the panels that are placed end to end that comprise a projecting portion relative to said theoretical continuous surface at the junction.
  • the theoretical continuous surface 46 is determined by taking measurements, for example, on either side of the junction on the periphery of the nacelle.
  • a shallow groove 48 is made relative to the theoretical continuous surface 46 , which extends, along a cutaway that is perpendicular to the junction, over a width on either side of said junction, approximately from the point of divergence between the outside surface of the panel of the lip 36 before machining and the theoretical continuous surface 46 , up to the point of divergence between the outside surface of the panel of the outside surface 34 before machining and the theoretical continuous surface 46 , as illustrated in FIG. 7B .
  • This groove 48 extends over the entire periphery of the nacelle, over 360°.
  • the width of the groove is such that the coating covers the attachment means.
  • a coating 50 is arranged in the groove 48 in such a way as to fill it in.
  • the thickness of the coating 50 is approximately equal to the depth d of the groove so that the outside surface of said coating assumes the shape of the theoretical continuous surface, as illustrated in FIG. 7C .
  • the coating 50 comprises a piece of sheet metal 52 that is also called a hoop, with a relatively small thickness, approximately equal to the depth of the groove 48 , and with a width that is approximately equal to that of the groove 48 so as to assume perfectly the shape of said groove 48 .
  • the piece of sheet metal 52 is stretched during the deposition and held by tension once attached so that its outside surface is essentially merged with the theoretical continuous surface 46 .
  • the piece of sheet metal 52 is shaped in advance on a mold.
  • This piece of sheet metal 52 comprises an attachment zone for closing the hoop, representing a reduced zone that is likely to generate negligible turbulence relative to the gain in laminarity provided.
  • This attachment zone can be replaced by a polished welding bead that considerably limits the generation of turbulence.
  • the piece of sheet metal 52 can be metallic. Its material is selected so that its expansion coefficient is adapted to those of the other adjacent elements of the nacelle.
  • the coating 50 is obtained by the application of a film or a paint 54 whose purpose is to fill in the groove 48 in such a way that the outside surface of the coating 50 is essentially merged with the theoretical continuous surface 46 .
  • the coating 50 is a silicone-based anti-corrosion paint, whereby said paint is applied by any suitable means in one or more layer(s) based on the thickness of the groove 48 .
  • the material of the coating is selected in such a way as to have a certain elasticity so as to adapt to dimensional variations arising from the expansion phenomena.
  • the space between the panels can be filled in with the same material as the coating or with another material.
  • the application of a film or a paint does not require an attachment as in the case of a hoop, which makes it possible to optimize the laminarity.
  • the coating 50 in particular the piece of sheet metal 52 , is perforated and preferably microperforated for allowing a stream of air to run through said coating 50 .
  • a cavity 56 is provided under the coating 50 in such a way as to collect the air that runs through said coating, whereby this cavity extends over at least a portion of the periphery and preferably over the entire periphery.
  • At least one pipe 58 connects this cavity to at least one opening 60 that empties into the inside pipe 32 .
  • the openings 60 have shapes that are suitable for ejecting air into the inside pipe 32 in a tangential manner to the surface of said pipe in the direction of flow of the stream of air channeled through the air intake of the nacelle.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
  • Exhaust Silencers (AREA)
US12/996,446 2008-06-06 2009-06-03 Method of depositing a coating for improving laminar flow Abandoned US20110168852A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0853758A FR2932106B1 (fr) 2008-06-06 2008-06-06 Procede de depose d'un revetement visant a ameliorer l'ecoulement laminaire
FR0853758 2008-06-06
PCT/FR2009/051048 WO2010001008A1 (fr) 2008-06-06 2009-06-03 Procede de depose d'un revetement visant a ameliorer l'ecoulement laminaire

Publications (1)

Publication Number Publication Date
US20110168852A1 true US20110168852A1 (en) 2011-07-14

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US12/996,446 Abandoned US20110168852A1 (en) 2008-06-06 2009-06-03 Method of depositing a coating for improving laminar flow

Country Status (5)

Country Link
US (1) US20110168852A1 (fr)
EP (1) EP2304204B1 (fr)
CN (1) CN102057144B (fr)
FR (1) FR2932106B1 (fr)
WO (1) WO2010001008A1 (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120037760A1 (en) * 2010-08-15 2012-02-16 Koppelman Henry J Laminar flow panel
US20120091285A1 (en) * 2010-10-15 2012-04-19 Airbus Operations (S.A.S) Aircraft nacelle including a continue joint area between an outer wall and a front frame
US20120280090A1 (en) * 2011-01-26 2012-11-08 Rolls-Royce Plc Connecting device particularly adapted for the connection between an air intake and an engine of an aircraft nacelle
US20120318924A1 (en) * 2011-06-17 2012-12-20 Airbus Operations Sas Air intake of an aircraft nacelle that incorporates a reinforced lip with a defrost system by joule-effect
US20150129045A1 (en) * 2013-11-11 2015-05-14 The Boeing Company Nacelle inlet configuration
US20150260104A1 (en) * 2014-03-15 2015-09-17 The Boeing Company One piece inlet lip skin design
US10189572B2 (en) * 2016-05-02 2019-01-29 The Boeing Company Systems and methods for preventing ice formation on portions of an aircraft
US10556670B2 (en) 2010-08-15 2020-02-11 The Boeing Company Laminar flow panel
US11027818B2 (en) 2017-08-30 2021-06-08 Airbus Operations S.A.S. Method for manufacturing an aircraft leading edge panel that allows extensive laminar flow to be obtained, and leading edge comprising at least one panel obtained using the said method
US11673681B2 (en) * 2019-08-13 2023-06-13 Airbus Operations Sas Anterior part of a nacelle of an aircraft propulsion assembly having a thermal transition region
JP7406388B2 (ja) 2019-02-26 2023-12-27 ザ・ボーイング・カンパニー 曲面部材のための隔壁用シム
DE102021105806B4 (de) 2021-03-10 2024-04-11 Deutsches Zentrum für Luft- und Raumfahrt e.V. Aerodynamischer Profilkörper für Luftfahrzeuge

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US8974177B2 (en) * 2010-09-28 2015-03-10 United Technologies Corporation Nacelle with porous surfaces
US8752795B2 (en) 2010-11-23 2014-06-17 John Ralph Stewart, III Inlet nose cowl with a locally thickened fastening portion to enable an uninterrupted airflow surface
DE102011116853A1 (de) 2011-10-25 2013-04-25 Merz Dental Gmbh Zahnsatzformblock zur Herstllung eines Zahnersatzteils und Verfahren zur Herstellung eines Zahnersatzteils
CN109606708B (zh) * 2018-12-03 2022-04-08 江西洪都航空工业集团有限责任公司 一种小尺寸进气道结构制备方法

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US4443990A (en) * 1982-03-11 1984-04-24 Johnson Wilfred B Method of producing crack free logs
US4630168A (en) * 1985-12-16 1986-12-16 The Boeing Company Lightning protection fastener
US4796153A (en) * 1987-06-01 1989-01-03 Lightning Diversion Systems Lightning diversion strips for aircraft
US5435889A (en) * 1988-11-29 1995-07-25 Chromalloy Gas Turbine Corporation Preparation and coating of composite surfaces
US5014934A (en) * 1989-06-30 1991-05-14 The Boeing Company Removable seal for discontinuities in aircraft skin
US5065960A (en) * 1990-02-05 1991-11-19 Northrop Corporation Gap filler for advanced aircraft to reduce radar detectability
US5427332A (en) * 1993-11-10 1995-06-27 The B. F. Goodrich Company Modular ice protection assembly
US5645886A (en) * 1994-01-19 1997-07-08 Lockheed Fort Worth Company Method and system for sealing a radiofrequency signal absorbing coating
US5476340A (en) * 1994-12-21 1995-12-19 Contrasto; Sam Method of using internal metal stitching for repairing cracks in concrete
US5771557A (en) * 1996-11-21 1998-06-30 Contrasto; Sam Concrete internal metal stitching
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US6328258B1 (en) * 1998-12-21 2001-12-11 Aerospatial Natra Air intake structure for aircraft engine
US6294261B1 (en) * 1999-10-01 2001-09-25 General Electric Company Method for smoothing the surface of a protective coating
US20010003897A1 (en) * 1999-12-21 2001-06-21 Alain Porte Device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit
US6385836B1 (en) * 2000-06-30 2002-05-14 Lockheed Martin Corporation Method for composite material repair
US7915371B2 (en) * 2002-06-07 2011-03-29 The Boeing Company Method and composition for sealing components and components sealed thereby
US7413764B2 (en) * 2004-06-14 2008-08-19 Northrop Grumman Corporation Process for repairing coatings having a critical thickness
US20060145001A1 (en) * 2004-12-30 2006-07-06 Smith Matthew C Fan cowl door elimination
US8282042B2 (en) * 2009-06-22 2012-10-09 The Boeing Company Skin panel joint for improved airflow
US8393578B2 (en) * 2009-06-22 2013-03-12 The Boeing Company Skin panel joint for improved airflow
US20120267473A1 (en) * 2009-09-09 2012-10-25 Tony Shuo Tao Elevon control system

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120037760A1 (en) * 2010-08-15 2012-02-16 Koppelman Henry J Laminar flow panel
US8783624B2 (en) * 2010-08-15 2014-07-22 The Boeing Company Laminar flow panel
US10556670B2 (en) 2010-08-15 2020-02-11 The Boeing Company Laminar flow panel
US10370090B2 (en) 2010-08-15 2019-08-06 The Boeing Company Laminar flow panel
US20120091285A1 (en) * 2010-10-15 2012-04-19 Airbus Operations (S.A.S) Aircraft nacelle including a continue joint area between an outer wall and a front frame
US20120280090A1 (en) * 2011-01-26 2012-11-08 Rolls-Royce Plc Connecting device particularly adapted for the connection between an air intake and an engine of an aircraft nacelle
US20120318924A1 (en) * 2011-06-17 2012-12-20 Airbus Operations Sas Air intake of an aircraft nacelle that incorporates a reinforced lip with a defrost system by joule-effect
US8794572B2 (en) * 2011-06-17 2014-08-05 Airbus Operations S.A.S. Air intake of an aircraft nacelle that incorporates a reinforced lip with a defrost system by joule-effect
US9663238B2 (en) * 2013-11-11 2017-05-30 The Boeing Company Nacelle inlet lip skin with pad-up defining a developable surface having parallel ruling lines
US20150129045A1 (en) * 2013-11-11 2015-05-14 The Boeing Company Nacelle inlet configuration
US9664113B2 (en) * 2014-03-15 2017-05-30 The Boeing Company One piece inlet lip skin design
AU2014274531B2 (en) * 2014-03-15 2018-05-10 The Boeing Company One piece inlet lip skin design
AU2014274531C1 (en) * 2014-03-15 2018-11-22 The Boeing Company One piece inlet lip skin design
US20150260104A1 (en) * 2014-03-15 2015-09-17 The Boeing Company One piece inlet lip skin design
US10189572B2 (en) * 2016-05-02 2019-01-29 The Boeing Company Systems and methods for preventing ice formation on portions of an aircraft
US11027818B2 (en) 2017-08-30 2021-06-08 Airbus Operations S.A.S. Method for manufacturing an aircraft leading edge panel that allows extensive laminar flow to be obtained, and leading edge comprising at least one panel obtained using the said method
JP7406388B2 (ja) 2019-02-26 2023-12-27 ザ・ボーイング・カンパニー 曲面部材のための隔壁用シム
US11673681B2 (en) * 2019-08-13 2023-06-13 Airbus Operations Sas Anterior part of a nacelle of an aircraft propulsion assembly having a thermal transition region
DE102021105806B4 (de) 2021-03-10 2024-04-11 Deutsches Zentrum für Luft- und Raumfahrt e.V. Aerodynamischer Profilkörper für Luftfahrzeuge

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CN102057144B (zh) 2013-09-11
FR2932106A1 (fr) 2009-12-11
EP2304204B1 (fr) 2016-03-30
CN102057144A (zh) 2011-05-11
EP2304204A1 (fr) 2011-04-06
FR2932106B1 (fr) 2010-05-21
WO2010001008A1 (fr) 2010-01-07

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